Aeroplane.



J. 6L W. SHARP.

AEROPLANE.

APPLICATION man JuNEso. 1911.

Patented Apr. 4, 1916.

1' L W- SHARP.

AEROPLANE.

APPLICATION FILED lUNEQ. 19H. 1,177,656. Patented. Apr. 4,1916.

4 SHEETSWSHEET 2.

L (y W. SHARP.

AEROPLANE.

" 'l APPUCATON FILED )UNE 30| 191- i L'VS, Patented Apr. 4,1916.

4 SHEETS-SHEET 3- 1. & W. SHARP. AROPLANE;

. PPLICTION FILED JUNE 30, )911. 1,177,656. Patented Apr. 4, 1916.

4 SHEETS-SHEET 4.

UNITED Asri-ifrias PATENT osi'iioi.

'..JOHN SHARP AND WILLIAM SHARP, OF CLEVELAND, OHIO.

AEROPLANE.

.270 tilt iti/0m may concern ...Be it known that we, .lonav Sir-ini' and YVIILLIAM Snam), citizens ot' the United States; and residents of tleveland.r in the vcounty ot' Cuyahoga and State of Ohio,

vide a self propelling aeroplane preferably of the iiionoplane typein which are provided improveddevices for obtaining stability ot' the machine under conditions ot' air currents varying inintensity ot' pressure and changeable in direction.I and also to provide Steering, elevating. and depressing devices ofgreat simplicity in construction and cfficiency andpracticability in use.

`The invention also has reference to automatically acting means for adjusting the Y balancing devices which are operatively con'- neeted with theseat ot' the driver whereby -tlie weight ot' the driver will place the. inachine in equilibrium as it is automaticallyu` shifted, by variationsin the angular `position of the machine in the air and thc etioi't of the driver to maintain his position will operate the balancing mechanism.

y Other features of the invention comprise `the construction oie the frame with trussed supports in lieu of stay wires, which rigidly secure the, planes and also comprise the specific character and construction of the operating mechanism for the balancing and lifting and depressing planes and steering devices, and the corrugated or transversely and closely veined or ribbed main and tioating planes and propeller. whereby a more,

-intiniate engagement witlr the `airr can be` etl'ected,

therein.

The invention further comprises the conibination and arrangement of parts and construction ofdetails hereinafter described, shown in the.accompanying drawingsand to; prevent slipping or sliding :spyeijcally` pointed out in the claims. to

n the accompanying` drawings lFigure is a plan View of the aeroplane; Fig. 2 1s a side elevation thereof ;f Fig. 3 is a front Specification of Letters Patent.

`Patented Apr. 4, 191th Application led June 30, 1911. Serial No. 636,275. l

elevation thereof; Fig; 4 is a longitudinal section through the steering head showing the devices operatively connected with Ythe tion on line fi--a Fig. l; Fig. tvis a longitudinal horizontal central section ot' the steering head; Fie'. Tis a transverse section of a-portion oi the main supporting` plane showing the corrugated arrangement thereot; Fig. 8 is a transverse section ot one of the planes; showing ribbed construction ot wood and silk; Fie'. t) is a longitudinal sec. i

tion ot a plane formed oi wood and silk;`

-Fig. l() is a front elevation. showing the main plane composed entirely ot' pivoted balancing planes; Fig. 11 is a side elevation of one oiLl the wheels` and bearing therefor l for use on land; Fig. ll is a 'front elevation thereof; Fig. 12 is a transverse.section ot the diamond trame showing a `seat for the operator depending trom thebridge and operating means t'or the several steeringA and balaiicingalcviccs operatively connected with the scat support; Fie'. 12 is aneularged perspective view ot the controlling mechanism; Fig. 13 is a plan view ot' the corrugated propeller; Fig. '14 is a side elei vation thereof; `Figfl is a troni. elevation.

of a inoditied form in which two main supporting planes are crossed to provide greater area of supporting surface; Fig. lt isa front elevation showing a trussed toi-m of wing or main plane; Fig. 17 is a side view of a trussed inner end; Fig.l 1S is a Side. view of a trussed outer end; Fig. 1t) isa sideelcvation ot' a portion ot' the trout end of the. traine showing location of engine and of the., plane which `.controls the.. angle of flying when descending or rising;lFig. 20 1s a perspective view ot' an aeroplane embodying our invention.

'In these views a triangular trame coinposed of side barsl, 1 and lower central bar 2 connected by struts, 2, forms the body who is seaend in :a cent al position between the side bars'and preferably on the lower bar at 4.

ably a slight curvature underneathto give laterally extending rods L, L rigidly seframe.

a constant tendency to elvate the front end of the frame. Their rear ends are preferably extended below the driver seat as shown in Fig. 2. These planes are mounted on cured to the upper bars 1, 1, These planes extend laterally on each side of the frame and preferably are separated to leave the aeroplane open on the longitudinal center thus giving theoperator a free view above the supporting planes in all directions, and rendering the danger of collision less imminent and giving the driver opportunity for perfect control of the aeroplane while giving a low point of center of gravity for his seat. y

The main supporting lanes may be rigidly secured by means ci) tension or stay wires`8, 8, and 9,- 9 attached to an elevated central bridge 10, which extends over the Blanes andfdrivers seat, and with itsbracev ars 11, 11 forms with the triangular body a diamond shaped front portion of 'great rigidity and lightness of construction.

The rear edges of the iront planes widen as they approach'the frame, having relaw tively narrower outer tips 12, 12 to which the sta wires 8, 8 and 9, 9 are attached. A lateral y extending rigid rear or floating plane 13 is horizontally attached to-the rear of the frame and is also preferably inclined to give a lifting impulse to the rear of the It is supported by transverse bars 14.-, 14 and is also closely and transversely ribbed or corrugated to aid in effecting frictional engagement with the air and to prevent slipping.

Two directing rudders 15,15 are shown at the rear of the machine pivoted on posts 16, 16 mounted on one of the bars 14 and connected together at their rear edges so as to move in unison. The -position of these `rudders underneath the horizontal keel plate-l3 enables the air to have immediate 'effect thereon as it passes underneath this machine which is apt to be occasioned by .l position of the front end of the driver andattaching the elevating and depressing planes to the front part of the machine. .By attaching these planes to the rear extremity however the rear portion can rise and fall without immediately. changing the B at right angles.

trol.

The equilibrium of thenaero lane is main` tained by` means of tilting ongitudinally placed narrow `planes 19, 19 which-may be.'

pivoted only in the extreme outer edges of the main supporting planes as shownfi'n" Figs. 1 and 3, or mayV compose the entire supporting surface of the'planes as shown in Fig. 10.

The planes by means of which the direction, elevation, depression and equilibrium of the machine are controlled are operable by the driver while seated in the frame and are connected preferabl Iasshown with 4a common steering post accessible to the hands of the driver.` y

The rudder planesV 15 are operated by mea-ns ofcords or wires W, W 'whichpass through suitable eyes E, E on the frame and are attached to the ends ofswinging arms A, A upon a central rod `R in the post Pv so that by turning a hand wheel 'H the driver can 'readily direct the ,movef ments of the aeroplane. The elevatingl and depressing plane is connected-by means orf.

wires F', F with the horizofgit'al sliding'bar B, which is movable vertically upIl ,and

down in guides B', B uponl Znplate Bf,

secured in the frame in front of the drivey The bar can be raised or lowered by raisingfk or lowering the front extremityy or toe T of the steering post, which' engages a 'slot' inthe bar B. For this purpose the steering post is mounted in aj'pivotal or@ 10d4 universal bearing Z which 'permits of movement 'in two directions and the operator can l elevate or depress the front end vof the post at will, to adjust the ition of the elevating and depressing a'ne.

The pivoted or tilting` p aries by means of tot which the equilibrium of the machinerie controlled are connected by means of wires. X, X to a. vertical bar' V crossing the 'bar` I This bar Y is. slotted at V and the toe T passes also through' the" slot V and when laterally moved' will g planes just as de scribed. To make this movement an auto-j operate the balancing matic one in which the members B' and Vf can be moved by the action ofv the body of theoperator, the seat 4 is' suspended by means .of a han'er J and a universal pivotal bearing fsecured intermediateof the upper bar .10 and lower barv 2 of the,l frame, so that the body will swing freely.;

To the upper end of the hanger is attachi; ed a projection or toe J similar to the'y projection T upon the post Py shown vin Fig:-J

(5, which acts in a similarl manner upon f crossedbars Bs and IB4 overhead, which arealso similarly slotted' so that the toe wil'lf extend through both of them at the crossing point. These barsare respectively con.-

L with lthe balancing `Yanes and felen nanddepressing planes 4toopei'ate n n @The steering@ wheel,` H is thentein- 1 loyed only for operating the rudder. i n; Figs.` 13 and 14 tliecorriigatedf conction" of lp'tlie propeller; blade islshown, ereby a, more: lingering contact with the l isjobtaineda In Fig. the;` planes by n means of` which the `aeroplaneHisvsupported i tlieair areslioiwn; separated into a series otjsections or smaller planesfllpivoted for angular adjustment in the side @bars` ofthe mainllplane. These smalleiaplanes 1 are attached together and are simultaneously sidelof` the central `l'iiaii'ie-are closing those n `the other side are epening, thus allording iimediate reliefs from sudden pressure oi' `keep, `the machine in` equilibrium, with `little The planes fsliown 1n"tli1s` ligure in no particular from the pivotecl :tli niainplanes, but are greateruin"number obtain apqiiicker eilect.` n

of tlieinpwliichare secured `Iwires neet-,nighA their outeig endsl and` stay flliis cpnstruction,"greatly ncreases the buoyancy of"*tlie-ai"oplane.

p `i`whichthe aeroplane is supported when ieient and comprises the brackets "O, each aving a Cylindrical vertical sleeve lD" ached `thereto in which is mounted rod `O2 n uglivvliichand itlii'ough slotsOain the lee'` `O,*O,",r.p"asses the shaft Of lupon n thewlieel()4A is mounted; Springs ",ve resiliency to theishaft when the light oftlie aeroplane bearsA thereon.` v

videdl witliitriangular trusses` whichsup` t them rigidly,land no guy Wires arenecifry altliou ghj they lean be used for greater l ety if desired to connect theubridge and p ieredge. "Inthese views rods C are conted with] the rods M` andL byineans of rutsff D, Dythus forininga trian ulai' tan pt ing truss abletoljsupport itsel rigidly.

on ated so rthatfivhile: the fplanesfon, oiie`` mists of wind and" enablingfthe operator to `plines` shown inllni'. 3 at the outer ends of i Innilig. anpaeroplanefs shown where `siipportmg surface of the `inainnplanes` Figsqllfandpll` are shown a"slioelc bing device `for the running `wheels l aliglits.` This `device is ""sirnple and i In Figs, 16, 17 and 18 are *shownplanes Th WiresyNf, N" strengthen theouter edges,

en the sidebars ofthe frameinfrent of the same, and can be controlled by any convenient means accessible` to the operator.

Having described the invention what `We `claim as new and desirev to `secure by Letters Patent is: 4 i, l,

1. In an aeroplane, a mainl fame, main Vhorizontally extending planes ,securedA toA said frame at the trent ot' the machine, balancing fanes pivoted in said main planes,

` an elevating and depressing vane pivoted `in respectively vertical and horizontal .di-

rections, flexible connections 'between said `vertical bar and said balancing vanes,

flexible connections"between said horizon? tal bar and said elevating and depressing vane, an operating'lever for both said bars, said lever provided with a projection en'- tering and slidingly movable in the slots in said bars, a vertical rudder and connections between said lever and said rudder adapted tc voperate the. rudder when `the l lever is turned on its longitudinal axis and adapted also to ope ate the rudder to.` some extent when the lever is moved about a transverse axis to operate the balancing planes.

2. In an aeroplane, a main frame, mainA lateral planes secured to the front of the frame, pvoted balancing varies therein, aV

horizontal elevating and depressing vane `pivoted in the rear of said frame, a vertical rudder pivoted in the rear oi said frame and an operating device for said varies and rudder comprising a support transversely secured in said frame, vertically and horizontally movable members sliding upon said support, said members being longitudinally slotted, a steering post, arms carried from Sie said post, an extension of said post passing through the slots in both said sliding menibei's, a supportin said frame intermediate `ef the ends of said post, in which support said steering post has universal movement, and flexible connections between said horizontally sliding member andsaid balancing varies and between said elevating and de-y y pressing vane. and said vertically movable member, `and between said arms and said rudder, said connections beingvadapted to operate the rudder and the balancing vanes" simultaneously;

3. The combination with the f'aine and laterally extending main planes, pivoted balancing vanes in said main planes, an ele- Vvaftiiig''aiid depressing vane and a rudder,`

illA a support in said frame, a post having la universal movement in said support, *slotted 'and' crossing members engaged at their cossingpoint by said post, and opfeltllcd` thereby, one member slidably movslidej at riglitangles torthe other member,

said members respectively and operatively i In testimony whereof, we hereunto set connected-with said vanes, mechanism roour hands this 8th day of October, 1910. 1) tatable upon said post for operating said T p rudder, the arrangement being such that the rudder may be operated independently t of the balancing vanes, but is operated to In presence ofsome extent upon operatlon of the balanc- WM. M. MONROE 3 lng venes. P. BREDEL. 

